32. Air flow is discharged to sea level atmosphere through a sonic nozzle. If the air storage pressure at the reservoir is 40x105 N/m2, determine the pressure, temperature density at the exit of the nozzle. Assume that the reservoir air is at ambient temperature. (6)

33. Derive an expression connecting area and velocity variations with Mach number for a one-dimensional compressible flow. (8)

34. Explain with suitable sketches the effect of pressure ratio on flow in a Laval nozzle.(8)

35. Sketch the pressure variation along a Laval nozzle for different back pressures. (6)

36. An airplane flying at 1500 kmph at an altitude where the pressure and temperature are respectively 3x104 N/m2 and -50 degree C. Calculate the pressure, density and

temperature at the leading edge of the wing. (10)

37. What is Rayleigh’s correction for total pressure measurement in supersonic flows? Why is the correction required? (8)

47. If a compression corner of angle 20 degree is allowed to encounter an uniform stream of supersonic flow at Mach 5, calculate the shock wave angle and pressure & Mach number behind the shock wave. (8)

48. Explain shock reflection from a solid boundary with a suitable sketch. (6)